摘要
通过风洞试验，利用７孔探头对７５°／４５°和７５°／６０°两种典型双三角翼进行了空间流场测量，研究了双三角翼前缘形状对大迎角涡流特性的影响．试验结果表明，双三角翼外翼前缘钝化使双涡态的双三角翼内、外翼涡互相靠拢、增加干扰，当出现合并涡态时，使合并涡涡核向内下方偏移；外翼前缘钝化使外翼涡或合并涡的Ｃｐ０、Ｖｘ较尖前缘时为高，最终使外翼涡或合并涡推迟破裂．
An experimental study is presented that has been caried out in a low speed wind tunnel on tow double delta wing models having leading edge sweep angles of 75°/45° and 75°/60°. The study has been conducted to investigate the effects of the wing leading edge shape on the vortex flow characteristics by using flowfield measurement. The test results indicate that the outboard leading edge of the double delta wing being blunted causes inboard vortex and outboard vortex close each other and stronger interaction and results in the merged vortex moving inward and downward at high angles of attack. The blunted outboard leading edge induces higher total pressure coefficient and axial velocity of the outboard vortex core or joined vortex core than that generated by the corresponding sharp leading edge wing, hence the bursting of the outboard vortex or joined vortex is delayed.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
1997年第3期341-345,共5页
Journal of Beijing University of Aeronautics and Astronautics
基金
航空科学基金
关键词
分离流动
涡旋流动
大迎角
三角翼
机翼
separated flow
double delta wings
vortex flow
high angle of attack
